Slot Effect on Wing Aerodynamic Performance, ANSYS Fluent Simulation Training

Description

Description

The present problem simulates the steady airflow over an airfoil (NACA4421) with a slot on the leading edge using ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The present model is designed in two dimensions using Design Modeler software. The meshing of this present model has been generated by Ansys Meshing software. The total cell number is 260000.

Methodology

In this project, steady airflow over an airfoil (NACA4421) is investigated By ANSYS Fluent software. Airfoil has a shape deformity (slot), which separates it into two different parts. A slot in the airfoil industry is used to optimize airfoil performance, including increased lift force.

The airfoil attack angle is equal to zero degrees. Air enters the domain with a velocity equal to 10 m/s. The drag and lift coefficients of this airfoil with zero attack angle are equal to 0.0755 and 0.3764, respectively.

Moreover, the standard k-epsilon model is enabled to solve the fluid equations.

Conclusion

At the end of the solution process, we obtain two-dimensional contours related to pressure, velocity, and eddy viscosity. For instance, the stagnation point in the pressure contour is evident where the pressure increases drastically at the airfoil’s leading edge.

Furthermore, by extracting detailed data using Fluent, Drag and lift coefficients of this airfoil are calculated to be equal to 0.0755 and 0.3764, respectively. Drag and lift coefficients for NACA4421 airfoil without slot with zero attack angles are reported to be equal to 0.06 and 0.1, respectively.

Both drag and lift coefficients are increased due to the presence of the slot.